发明名称 |
AIRCRAFT LEADING EDGE DEVICE SYSTEMS AND CORRESPONDING SIZING METHODS |
摘要 |
<p>Aircraft leading edge device systems and methods for sizing such systems are disclosed. In one embodiment, a spanwise lift coefficient distribution for an airfoil corresponding to at least one design condition and at least one aircraft angle of attack is identified, and a leading edge device chord length is sized to at least approximately achieve the selected spanwise lift coefficient distribution. In another embodiment, a spanwise distribution of aircraft angles of attack corresponding to local maximum lift coefficients for an airfoil operated at a design condition is identified, and a leading edge device chord length at each of a plurality of spanwise locations is sized to achieve the distribution of aircraft angles of attack corresponding to local maximum lift coefficients. In yet another embodiment, a leading edge device chord length is tapered in two, at least approximately opposite, spanwise directions.</p> |
申请公布号 |
WO2005092703(A1) |
申请公布日期 |
2005.10.06 |
申请号 |
WO2005US05233 |
申请日期 |
2005.02.22 |
申请人 |
THE BOEING COMPANY;LACY, DOUGLAS, S.;WYATT, GREG, H. |
发明人 |
LACY, DOUGLAS, S.;WYATT, GREG, H. |
分类号 |
B64C9/24;(IPC1-7):B64C9/24 |
主分类号 |
B64C9/24 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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